WO2018045575A1 - Ensemble hélice, système de puissance et véhicule aérien - Google Patents

Ensemble hélice, système de puissance et véhicule aérien Download PDF

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Publication number
WO2018045575A1
WO2018045575A1 PCT/CN2016/098612 CN2016098612W WO2018045575A1 WO 2018045575 A1 WO2018045575 A1 WO 2018045575A1 CN 2016098612 W CN2016098612 W CN 2016098612W WO 2018045575 A1 WO2018045575 A1 WO 2018045575A1
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WO
WIPO (PCT)
Prior art keywords
blade
propeller
attack
angle
common axis
Prior art date
Application number
PCT/CN2016/098612
Other languages
English (en)
Chinese (zh)
Inventor
王佳迪
张永生
梁贵彬
陈星元
Original Assignee
深圳市大疆创新科技有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to PCT/CN2016/098612 priority Critical patent/WO2018045575A1/fr
Priority to CN201680065838.6A priority patent/CN108463406A/zh
Publication of WO2018045575A1 publication Critical patent/WO2018045575A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B64C27/10—Helicopters with two or more rotors arranged coaxially
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/467—Aerodynamic features

Definitions

  • Embodiments of the present invention relate to the field of power, and more particularly to a propeller assembly, a power system, and an aircraft.
  • a propeller is a device that relies on a blade to rotate in a transmission medium such as air or water to convert the engine's rotational power into thrust or tension. It is widely used in the power system of aircraft, submarines and other devices. Taking a multi-rotor aircraft as an example, in order to obtain greater lift with the same projection size, a coaxial twin-blade propeller design is generally used, that is, two layers of propellers are arranged at upper and lower intervals along the same axial direction.
  • the airflow generated by the upper blade during the rotation will enter the lower blade, resulting in the flow velocity of the lower blade being much higher than the flow velocity of the upper blade.
  • the upper blade and the lower blade generally adopt the same angle of attack design, and the above airflow velocity difference may cause the upper blade and the lower blade to fail to achieve the expected working effect.
  • the paddle efficiency of the lower blade is greatly lost due to the difference in the air flow rate described above.
  • Embodiments of the present invention provide a propeller assembly, a power system, and an aircraft to solve the effect on the working effect of the propeller due to the difference in airflow velocity between the blades of different layers.
  • a technical solution adopted by the embodiment of the present invention is to provide a propeller assembly including a first propeller and a second propeller disposed at intervals, the first propeller including the first hub and the first hub At least one first blade, the second propeller includes a second hub and at least one second blade connecting the second hub, during the rotation of the propeller assembly, the accelerated airflow generated by the first propeller rotation process is from the first The propeller points and acts on the second propeller, and the radial angle of attack of the second blade is different from the radial angle of attack of the first blade.
  • the radial angle of attack adopted by the second blade makes the paddle efficiency of the second propeller more efficient than that of the second blade when the second blade adopts the radial angle of attack of the first blade .
  • the paddle efficiency of the second propeller depends on the magnitude of the pulling force generated when the second propeller rotates at a specific rotational speed.
  • the rotating shaft of the first propeller is coaxially arranged with the rotating shaft of the second propeller, and the first screw is At least a portion of the accelerated airflow generated by the spinner rotation process enters the second propeller from the first propeller.
  • the angle of attack of the second blade is greater than the angle of attack of the first blade.
  • the radius is first At a position of 25.9% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 10.4 ⁇ 0.5 degrees.
  • the radius is first At a position of 44.4% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 13.9 ⁇ 0.5 degrees.
  • the radius is first At a position of 63.0% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 8.4 ⁇ 0.5 degrees.
  • the radius is first At a position of 81.5% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 5.2 ⁇ 0.5 degrees.
  • the radius is first At a position 100% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 6 ⁇ 0.5 degrees.
  • one technical solution adopted by the embodiment of the present invention is to provide a power system including a propeller assembly and a motor assembly for driving the propeller assembly, the propeller assembly including the first propeller and the interval a second propeller, the first propeller includes at least one first blade, and the second propeller includes at least one second blade.
  • the accelerated airflow generated by the first propeller rotation process is directed from the first propeller and acts In the second propeller, the radial angle of attack of the second blade is different from the radial angle of attack of the first blade.
  • the radial angle of attack adopted by the second blade makes the paddle efficiency of the second propeller more efficient than that of the second blade when the second blade adopts the radial angle of attack of the first blade .
  • the paddle efficiency of the second propeller depends on the magnitude of the pulling force generated when the second propeller rotates at a specific rotational speed.
  • the rotating shaft of the first propeller is disposed coaxially with the rotating shaft of the second propeller, and at least a portion of the accelerating airflow generated by the first propeller rotating process enters the second propeller from the first propeller.
  • the angle of attack of the second blade is greater than the angle of attack of the first blade.
  • the radius is first At a position of 25.9% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 10.4 ⁇ 0.5 degrees.
  • the radius is first At a position of 44.4% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 13.9 ⁇ 0.5 degrees.
  • the radius is first At a position of 63.0% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 8.4 ⁇ 0.5 degrees.
  • the radius is first At a position of 81.5% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 5.2 ⁇ 0.5 degrees.
  • the radius is first At a position 100% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 6 ⁇ 0.5 degrees.
  • the motor assembly includes a first motor for driving the first propeller and a second motor for driving the second propeller.
  • one technical solution adopted by the embodiment of the present invention is to provide an aircraft including a power system and an arm supporting the power system, the power system including a propeller assembly and a motor assembly for driving the propeller assembly.
  • the propeller assembly includes a first snail spaced apart a propeller and a second propeller, the first propeller including at least one first blade, and the second propeller including at least one second blade, the acceleration airflow generated by the first propeller rotation process from the first during the rotation of the propeller assembly
  • the propeller points and acts on the second propeller, and the radial angle of attack of the second blade is different from the radial angle of attack of the first blade.
  • the radial angle of attack adopted by the second blade makes the paddle efficiency of the second propeller more efficient than that of the second blade when the second blade adopts the radial angle of attack of the first blade .
  • the paddle efficiency of the second propeller depends on the magnitude of the pulling force generated when the second propeller rotates at a specific rotational speed.
  • the rotating shaft of the first propeller is disposed coaxially with the rotating shaft of the second propeller, and at least a portion of the accelerating airflow generated by the first propeller rotating process enters the second propeller from the first propeller.
  • the angle of attack of the second blade is greater than the angle of attack of the first blade.
  • the radius is first At a position of 25.9% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 10.4 ⁇ 0.5 degrees.
  • the radius is first At a position of 44.4% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 13.9 ⁇ 0.5 degrees.
  • the radius is first At a position of 63.0% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 8.4 ⁇ 0.5 degrees.
  • the radius is first At a position of 81.5% of the distance between the outer end of the blade and the second blade and the common shaft, the difference between the angle of attack of the second blade and the angle of attack of the first blade is 5.2 ⁇ 0.5 degrees.
  • the radius is first At an angle of 100% of the distance between the outer end of the blade and the second blade and the common shaft, the angle of attack of the second blade and the angle of attack of the first blade The difference between the two is 6 ⁇ 0.5 degrees.
  • the motor assembly includes a first motor for driving the first propeller and a second motor for driving the second propeller.
  • the beneficial effects of the embodiments of the present invention are: in the propeller assembly, the power system and the aircraft provided by the embodiments of the present invention, the radial angle of attack of the different layers of blades is set to be different from each other, and the different layers of blades can be effectively avoided.
  • FIG. 1 is a partial perspective view of an aircraft using a propeller assembly in accordance with an embodiment of the present invention
  • Figure 2 is a side elevational view of the propeller assembly of Figure 1;
  • FIG. 3 is a schematic diagram showing a radial angle of attack example of a two-layer blade of a propeller assembly in accordance with an embodiment of the present invention
  • FIG. 4 is a top plan view of a two-layer paddle in accordance with another embodiment of the present invention.
  • Figure 5 is a schematic cross-sectional view of the two-layer paddle of the propeller assembly taken along line A-A of Figure 4;
  • Figure 6 is a schematic cross-sectional view of the two-layer paddle of the propeller assembly taken along line B-B of Figure 4;
  • Figure 7 is a schematic cross-sectional view of the two-layer paddle of the propeller assembly taken along line C-C of Figure 4;
  • Figure 8 is a schematic cross-sectional view of the two-layer paddle of the propeller assembly taken along line D-D of Figure 4;
  • Figure 9 is a schematic cross-sectional view of two layers of blades of the propeller assembly taken along line E-E of Figure 4;
  • FIG. 1 is a partial perspective view of an aircraft using a propeller assembly in accordance with an embodiment of the present invention.
  • the aircraft of the present embodiment includes an arm 11, a motor assembly 12 supported on the arm 11, and a propeller assembly 13 driven by the motor assembly 12.
  • the propeller assembly 13 includes a first propeller 131 and a second propeller 132 that are spaced apart.
  • the first propeller 131 includes a first hub 1311 and at least one first blade 1312 coupled to the first hub 1311.
  • the second propeller 132 includes a second hub 1321 and at least a second connected to the second hub 1321. Blade 1322.
  • the number of the first paddle 1312 and the second paddle 1322 is two.
  • the number of the two can be rooted. Arbitrarily set according to actual needs.
  • the rotation axes of the first propeller 131 and the second propeller 132 are coaxially disposed, and the motor assembly 12 includes two motors 121, 122 that drive the first propeller 131 and the second propeller 132, respectively.
  • the axes of rotation of the first propeller 131 and the second propeller 132 may be arranged in parallel, or the first propeller 131 and the second propeller 132 may also be driven by the same motor.
  • the propeller assembly 13 and the motor assembly 12 constitute the power system of the aircraft and provide the aircraft with the power required to fly through the rotation of the first propeller 131 and the second propeller 132.
  • FIG. 2 is a side view of the propeller assembly shown in FIG. 1.
  • the accelerated airflow generated by the rotation of the first propeller 131 is directed from the first propeller 131 and acts on the second propeller 132.
  • at least a portion of the accelerated airflow generated by the rotation of the first propeller 131 enters the second propeller 132 from the first propeller 131 in the direction indicated by the arrow, resulting in the first propeller 131 and the second propeller 132.
  • the airflow at the location has a certain flow rate difference.
  • the radial angle of attack of the second blade 1322 of the second propeller 132 is designed to be different first.
  • the radial angle of attack line refers to the curve of the angle of attack of the blade along the radial direction of the propeller.
  • FIG. 3 is a schematic diagram of a radial angle of attack example for a two-layer blade of a propeller assembly in accordance with an embodiment of the present invention.
  • the paddle efficiency of the second propeller 132 is lowered.
  • the paddle efficiency of the second propeller 132 depends on the amount of tension generated by the second propeller 132 at a particular rotational speed. In short, the greater the pulling force produced at a particular speed, the higher the efficiency of the paddle.
  • the first blade 1312 of the first propeller 131 selects the radial angle of attack line shown by the curve 10
  • the second blade 1322 of the second propeller 132 selects the radial direction shown by the curve 20.
  • Angle of attack line type In the two radial angle of attack types shown in FIG. 3, the angle of attack of the second blade 1322 at the same radial position of the common axis (origin) of the distance between the first propeller 131 and the second propeller 132 An angle of attack greater than the first blade 1312.
  • the second propeller 1322 can adopt the radial angle of attack type shown by the curve 20, and the second propeller 132 has the paddle efficiency higher than that of the second blade 1322.
  • the pitch of the second helical propeller 132 of the radial angle of attack shown by curve 10 is more efficient (eg, generated) The pulling force is greater), thereby overcoming the effect of the above-described airflow velocity difference on the paddle efficiency in the case where the first blade 1312 and the second blade 1322 are of the same radial angle of attack.
  • the above embodiment only illustrates the specific example of the first blade 1312 and the second blade 1322 by taking the paddle efficiency as an example.
  • the radial angle of attack of the 1312 and the second blade 1322 are set to be different from each other to achieve the desired working effect.
  • the above embodiment has been described by taking only two-layer paddles as an example, the embodiments of the present invention are applicable to other multi-layer paddle designs such as three-layer paddles and four-layer paddles.
  • FIG. 4 is a top plan view of a two-layer paddle according to another embodiment of the present invention, and FIGS. 5-9 are first taken at different radial positions of the first paddle 1312 and the second paddle 1322 shown in FIG.
  • a schematic cross-sectional view of the paddle 1312 and the second paddle 1322 compares the difference between the angle of attack of the first paddle 1312 and the second paddle 1322.
  • the first paddle 1312 and the second paddle 1322 are equally long and the outer ends of the first paddle 1312 and the second paddle 1322 are equidistant from the common axis, The specific distance is shown as L in FIG.
  • any of the first paddle 1312 and the second paddle 1322 can also be scaled in a practical application such that the actual length of the first paddle 1312 and the second paddle 1322 Inconsistent.
  • first paddle 1312 and the second paddle 1322 are equally scaled to be equal to each other, and the outer ends of the two are equidistant from the common axis, the first paddle 1312 and the second paddle 1322 The angle of attack between the two still meets the following range of numbers.
  • the angle of attack a22 of the second blade 1322 is 26.9 degrees
  • the angle of attack a21 of the first blade 1312 is 13.0 degrees
  • the difference is preferably 13.9 ⁇ 0.5 degrees.
  • the angle of attack a42 of the second blade 1322 is 14.0 degrees
  • the angle of attack a41 of the first blade 1312 is 8.8 degrees
  • the difference between the two is 5.2, and further consideration is made for manufacturing and equipment tolerances.
  • the difference between the two is preferably 5.2 ⁇ 0.5 degrees.
  • the angle of attack a52 of the second blade 1322 is 13.0 degrees
  • the angle of attack a51 of the first blade 1312 is 7.0 degrees
  • the difference between the two is 6 degrees, and further consideration is made between manufacturing and equipment tolerances.
  • the difference is preferably 6 ⁇ 0.5 degrees.
  • the radial angle of attack of different layer blades is set to be different from each other, and different layers can be effectively avoided.
  • the specific angle of attack design effectively avoids the influence of the difference in airflow velocity on the propeller.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention porte sur un ensemble hélice, un système de puissance et sur un véhicule aérien. L'ensemble hélice (13) comprend des premières hélices (131) et des secondes hélices (132) qui sont disposées à des intervalles. Chaque première hélice (131) comprend un premier moyeu d'hélice (1311) et au moins une première pale (1312) reliée au premier moyeu d'hélice (1311). Chaque seconde hélice (132) comprend un second moyeu d'hélice (1321) et au moins une seconde pale (1312) reliée au second moyeu d'hélice (1321). Pendant la rotation de l'ensemble hélice (13), des écoulements d'air d'accélération générés pendant la durée de la rotation des premières hélices (131) se dirigent vers les secondes hélices (132) depuis les premières hélices (131) et agissent sur les secondes hélices (132) de telle sorte que les types de ligne d'angle d'attaque radial des secondes pales (1322) soient différents de ceux des premières pales (1312). De cette manière, les types de ligne d'angle d'attaque radial des pales sur différentes couches sont définis de sorte à être différents les uns des autres et, par conséquent, les impacts de différence entre des vitesses d'écoulement d'air entre les pales sur différentes couches sur les effets de travail des hélices peuvent être évités de manière efficace.
PCT/CN2016/098612 2016-09-09 2016-09-09 Ensemble hélice, système de puissance et véhicule aérien WO2018045575A1 (fr)

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PCT/CN2016/098612 WO2018045575A1 (fr) 2016-09-09 2016-09-09 Ensemble hélice, système de puissance et véhicule aérien
CN201680065838.6A CN108463406A (zh) 2016-09-09 2016-09-09 一种螺旋桨组件、动力系统及飞行器

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PCT/CN2016/098612 WO2018045575A1 (fr) 2016-09-09 2016-09-09 Ensemble hélice, système de puissance et véhicule aérien

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022093109A1 (fr) * 2020-10-29 2022-05-05 ST Engineering Aerospace Ltd. Optimisation aérodynamique des conceptions de dimensionnement et de pale de rotors coaxiaux en corotation

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US5054998A (en) * 1988-09-30 1991-10-08 The Boeing Company, Inc. Thrust reversing system for counter rotating propellers
US20090026310A1 (en) * 2007-07-23 2009-01-29 Linn Romeo S Variable pitch anti torque coaxial counter rotation bi-prop rotor
CN104590556A (zh) * 2014-10-31 2015-05-06 湖北易瓦特科技有限公司 一种可折叠式无人机
CN105818975A (zh) * 2016-04-29 2016-08-03 湖北易瓦特科技股份有限公司 具有共轴双桨结构的多旋翼无人机
CN205440847U (zh) * 2015-12-25 2016-08-10 广州亿航智能技术有限公司 机臂可折放的多旋翼载人飞行器
CN206125417U (zh) * 2016-09-09 2017-04-26 深圳市大疆创新科技有限公司 一种螺旋桨组件、动力系统及飞行器

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US9688395B2 (en) * 2013-12-04 2017-06-27 Sikorsky Aircraft Corporation Boundary layer ingesting blade
CN105253295A (zh) * 2015-10-30 2016-01-20 深圳市道通智能航空技术有限公司 一种螺旋桨及飞行器
CN105270618B (zh) * 2015-11-04 2017-07-25 中航维拓（北京）科技有限责任公司 一种油动变距共轴六旋翼直升机
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Publication number Priority date Publication date Assignee Title
US5054998A (en) * 1988-09-30 1991-10-08 The Boeing Company, Inc. Thrust reversing system for counter rotating propellers
US20090026310A1 (en) * 2007-07-23 2009-01-29 Linn Romeo S Variable pitch anti torque coaxial counter rotation bi-prop rotor
CN104590556A (zh) * 2014-10-31 2015-05-06 湖北易瓦特科技有限公司 一种可折叠式无人机
CN205440847U (zh) * 2015-12-25 2016-08-10 广州亿航智能技术有限公司 机臂可折放的多旋翼载人飞行器
CN105818975A (zh) * 2016-04-29 2016-08-03 湖北易瓦特科技股份有限公司 具有共轴双桨结构的多旋翼无人机
CN206125417U (zh) * 2016-09-09 2017-04-26 深圳市大疆创新科技有限公司 一种螺旋桨组件、动力系统及飞行器

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022093109A1 (fr) * 2020-10-29 2022-05-05 ST Engineering Aerospace Ltd. Optimisation aérodynamique des conceptions de dimensionnement et de pale de rotors coaxiaux en corotation

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